Turbomachine combustor assembly including a liner stop

ABSTRACT

A turbomachine combustor assembly includes a combustor housing and a combustor body. The combustor body defines a combustor liner having a first end portion that extends to a second end portion through a combustion chamber. A cap assembly is mounted at the combustor housing. The cap assembly includes an endcover, a plurality of fuel nozzles supported by the end cover, and an outer barrel member. The outer barrel member extends about the plurality of fuel nozzles. A liner stop is arranged on one of the outer barrel member and the first end portion of the combustor liner. The liner stop includes a stepped lip portion that receives the other of the outer barrel member and the first end portion of the combustor liner to form substantially smooth liner to outer barrel interface. The liner stop restricts axial movement of the combustor liner relative to the outer barrel member.

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to the art of turbomachinesand, more particularly, to turbomachine combustor assembly including aliner stop.

In conventional turbomachines, a first fluid, such as fuel, is directedinto a combustor cap prior to being mixed with another fluid, such asair, and combusted in a combustion chamber to form hot gases. The firstfluid enters the combustor cap through a fuel manifold joined to thecombustor casing. Compressor discharge air passes through a passagewaythat extends between a cap liner and the combustion chamber into thecombustion cap to mix with the fuel. The cap liner is supported in aspaced relationship between the combustion chamber and an outercombustor casing. The combustion cap generally includes several linerstops that engage with the liner to restrict axial movement of the capliner during turbomachine operation.

BRIEF DESCRIPTION OF THE INVENTION

According to one aspect of the exemplary embodiment, a turbomachinecombustor assembly includes a combustor housing having a first end, anda combustor body arranged within the combustor housing. The combustorbody defines a combustor liner having a first end portion that extendsto a second end portion through a combustion chamber. A cap assembly ismounted at the first end of the combustor housing. The cap assemblyincludes an endcover, a plurality of fuel nozzles supported by the endcover, and an outer barrel member extending between the end cover andthe combustor housing. The outer barrel member extends about theplurality of fuel nozzles. A liner stop is arranged on one of the outerbarrel member and the first end portion of the combustor liner. Theliner stop includes a stepped lip portion that receives the other of theouter barrel member and the first end portion of the combustor liner toform substantially smooth liner to outer barrel interface. The linerstop restricts axial movement of the combustor liner relative to theouter barrel member.

According to another aspect of the exemplary embodiment, a turbomachineincludes a compressor portion, a turbine portion operatively connectedto the compressor portion, and a combustor assembly fluidly connectingthe compressor portion and the turbine portion. The combustor assemblyincludes a combustor housing having a first end, and a combustor bodyarranged within the combustor housing. The combustor body defines acombustor liner having a first end portion that extends to a second endportion through a combustion chamber. A cap assembly is mounted at thefirst end of the combustor housing. The cap assembly includes anendcover, a plurality of fuel nozzles supported by the end cover, and aflow sleeve extending between the end cover and the combustor housing.The flow sleeve includes an outer barrel member that extends about theplurality of fuel nozzles. A liner stop is arranged on one of the outerbarrel member and the first end portion of the combustor liner. Theliner stop includes a stepped lip portion that receives the other of theouter barrel member and the first end portion of the combustor liner toform substantially smooth liner to outer barrel interface. The linerstop restricts axial movement of the combustor liner relative to theouter barrel member.

According to yet another aspect of the exemplary embodiment, a method ofjoining a cap assembly to a turbomachine combustor housing includesaligning an outer barrel member carried by the cap assembly with acombustor liner extending about a combustion chamber in the combustorhousing, inserting a stepped lip portion provided on one of the outerbarrel member and the combustor liner into the other of the outer barrelmember and the combustor liner to form a liner to outer barrelinterface, and securing the cap assembly to the turbomachine combustorhousing.

These and other advantages and features will become more apparent fromthe following description taken in conjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWING

The subject matter, which is regarded as the invention, is particularlypointed out and distinctly claimed in the claims at the conclusion ofthe specification. The foregoing and other features, and advantages ofthe invention are apparent from the following detailed description takenin conjunction with the accompanying drawings in which:

FIG. 1 is a partial cross-sectional view of a turbomachine including acombustor assembly having a liner stop in accordance with an exemplaryembodiment;

FIG. 2 is a partial perspective view of a cap assembly portion of thecombustor assembly illustrating a liner stop in accordance with theexemplary embodiment;

FIG. 3 is detail perspective view of the liner stop of FIG. 2; and

FIG. 4 is a partial plan view of the liner stop of FIG. 2.

The detailed description explains embodiments of the invention, togetherwith advantages and features, by way of example with reference to thedrawings.

DETAILED DESCRIPTION OF THE INVENTION

The terms “axial” and “axially” as used in this application refer todirections and orientations extending substantially parallel to a centerlongitudinal axis of a combustor assembly. The terms “radial” and“radially” as used in this application refer to directions andorientations extending substantially orthogonally to the centerlongitudinal axis of the combustor assembly. The terms “upstream” and“downstream” as used in this application refer to directions andorientations relative to an axial flow direction with respect to thecenter longitudinal axis of the combustor assembly.

With reference to FIG. 1, a turbomachine in accordance with an exemplaryembodiment is indicated generally at 2. Turbomachine 2 includes acompressor portion 4 operatively connected to a turbine portion 6. Acombustor assembly 10 fluidly connects compressor portion 4 with turbineportion 6. Compressor portion 4 includes a compressor discharge 14 thatpasses compressor discharge air into combustor assembly 10. As will bediscussed more fully below, a portion of the combustor discharge air isemployed for cooling various components of combustor assembly 10, andanother portion of the compressor discharge air is mixed with fuel toform a combustible mixture that is combusted to form hot gases. The hotgases pass from combustor assembly 10 through a transition piece 16 intoturbine portion 6. Turbine portion 6 converts thermal energy from thehot gases into mechanical, rotational energy used to power varioussystems such as generators, pumps and the like.

In accordance with the exemplary embodiment shown, combustor assembly 10includes a combustor housing 20 having a first end 22 that extends to asecond end (not shown). Combustor assembly 10 includes a combustor body30 arranged within combustor housing 20. Combustor body 30 defines acombustor liner 34. Combustor liner 34 includes a first end portion 37that extends to a second end portion 38 through a combustion chamber 40.Combustor assembly 10 also includes an cap assembly 50 mounted at firstend 22 of combustor housing 20. Cap assembly 50 includes an end cover 52and a forward casing 53.

End cover 52 supports a plurality of fuel nozzles, one of which isindicated at 56, arranged in an annular array. Fuel nozzles 56 extendfrom end cover 52 toward combustion chamber 40. As will be detailed morefully below, fuel and air are mixed in forward casing 53 forming acombustible mixture that is passed to fuel nozzles 56. The combustiblemixture is combusted and expanded in combustion chamber 40 and thenpassed through transition piece 16 toward turbine portion 6. Forwardcasing 53 includes a body 60 having a first flange 62 that isoperatively connected to first end 22 of combustor housing 20 and asecond flange 63 to which is mounted end cover 52. Forward casing 53includes an outer barrel member 66 that extends about fuel nozzles 56and defines, in part, a passage (not separately labeled) that conductscompressor discharge air from combustor housing 20 toward end cover 52.

In accordance with an exemplary embodiment, outer barrel member 66includes a body member 67 having a first end section 68 that extends toa second end section 69. Second end section 69 abuts first end portion37 of combustor liner 34. In order to restrict axial movement ofcombustor liner 34, outer barrel member 66 includes a liner stop 80.Liner stop 80 includes a stepped lip portion 83 provided at second endsection 69 of outer barrel member 66. Stepped lip portion 83 includes afirst wall section 86 and a second wall section 87. First wall section86 extends from body member 67 radially toward a centerline (notseparately labeled) of combustor assembly 10. Second wall section 87 isradially offset from body member 67 and extends substantiallyperpendicularly from first wall section 86.

Cap assembly 50 is positioned at combustor housing 20 with outer barrelmember 66 being aligned with combustor liner 34. Cap assembly 50 ismounted and secured to combustor housing 20 with stepped lip portion 83extending into first end portion 37 of combustor liner 34 forming asubstantially smooth liner-to-outer barrel member interface 90. Withinthis arrangement, first wall section 86 restricts axial movement ofcombustion liner 34 while stepped lip portion 83 establishes a smoothtransition between combustion liner 34 and outer barrel member 66. Thesmooth transition established between combustion liner 34 and outerbarrel portion 66 promotes a substantially laminar flow of compressordischarge air passing from compressor portion 4 along combustor body 30.Thus, not only does liner stop 80 limit or restrict axial movement ofcombustion liner 34 but also conditions fluid flow to fuel nozzles 56.

In further accordance with the exemplary embodiment, liner stop 80 isprovided with a seal member 94 that includes a plurality of sealsegments, one of which is indicated at 96, secured to second wallsection 87 to form a hula seal 99. Seal member 94 restricts fluid flowpassing over combustion liner 34 toward end cover 52 from escapingthrough liner-to-outer barrel member interface 90. That is, when outerbarrel member 66 inserted into combustion liner 34, first end portion 37compresses seal member 84 to form a more robust seal at liner-to-outerbarrel member interface 90. At this point it should be understood thatwhile shown on outer barrel member 66, stepped lip portion 83 couldalternatively be formed on first end portion 37 of combustion liner 34.In addition, while shown with a seal member formed from multiple sealsegments, it should be understood that a continuous seal could also beemployed.

While the invention has been described in detail in connection with onlya limited number of embodiments, it should be readily understood thatthe invention is not limited to such disclosed embodiments. Rather, theinvention can be modified to incorporate any number of variations,alterations, substitutions or equivalent arrangements not heretoforedescribed, but which are commensurate with the spirit and scope of theinvention. Additionally, while various embodiments of the invention havebeen described, it is to be understood that aspects of the invention mayinclude only some of the described embodiments. Accordingly, theinvention is not to be seen as limited by the foregoing description, butis only limited by the scope of the appended claims.

1. A turbomachine combustor assembly comprising: a combustor housinghaving a first end; a combustor body arranged within the combustorhousing, the combustor body defining a combustor liner having a firstend portion that extends to a second end portion through a combustionchamber; a cap assembly mounted at the first end of the combustorhousing, the cap assembly including an endcover, a plurality of fuelnozzles supported by the end cover and an outer barrel member extendingbetween the end cover and the combustor housing, the outer barrel memberextending about the plurality of fuel nozzles; and a liner stop arrangedon one of the outer barrel member and the first end portion of thecombustor liner, the liner stop including a stepped lip portion thatreceives the other of the outer barrel member and the first end portionof the combustor liner to form substantially smooth liner-to-outerbarrel interface, the liner stop restricting axial movement of thecombustor liner relative to the outer barrel member.
 2. The turbomachinecombustor assembly according to claim 1, further comprising: a sealmember arranged at the substantially smooth liner to outer barrelinterface.
 3. The turbomachine combustor assembly according to claim 2,wherein the seal member is provided on the stepped lip portion.
 4. Theturbomachine combustor assembly according to claim 2, wherein the sealmember extends radially about the outer barrel member at the stepped lipportion.
 5. The turbomachine combustor assembly according to claim 2,wherein the seal member comprises a hula seal.
 6. The turbomachinecombustor assembly according to claim 1, wherein the substantiallysmooth liner-to-outer barrel interface is configured and disposed tocondition a fluid flow passing over the combustor liner toward the endcover.
 7. The turbomachine combustor assembly according to claim 6,wherein the stepped lip portion is configured and disposed to promote asubstantially laminar flow across the substantially smooth liner toouter barrel interface.
 8. The turbomachine combustor assembly accordingto claim 1, wherein the liner stop is provided on the outer barrelmember.
 9. A turbomachine comprising: a compressor portion; a turbineportion operatively connected to the compressor portion; and a combustorassembly fluidly connecting the compressor portion and the turbineportion, the combustor assembly comprising: a combustor housing having afirst end; a combustor body arranged within the combustor housing, thecombustor body defining a combustor liner having a first end portionthat extends to a second end portion through a combustion chamber; a capassembly mounted at the first end of the combustor housing, the capassembly including an endcover, a plurality of fuel nozzles supported bythe end cover and an outer barrel member extending between the end coverand the combustor housing, the outer barrel member extending about theplurality of fuel nozzles; and a liner stop arranged on one of the outerbarrel member and the first end portion of the combustor liner, theliner stop including a stepped lip portion that receives the other ofthe outer barrel member and the first end portion of the combustor linerto form substantially smooth liner to outer barrel interface, the linerstop restricting axial movement of the combustor liner relative to theouter barrel member.
 10. The turbomachine according to claim 9, furthercomprising: a seal member arranged at the substantially smooth liner toouter barrel interface.
 11. The turbomachine according to claim 9,wherein the seal member is provided on the stepped lip portion.
 12. Theturbomachine according to claim 9, wherein the seal member extendsradially about the outer barrel member at the stepped lip portion. 13.The turbomachine according to claim 9, wherein the seal member comprisesa hula seal.
 14. The turbomachine according to claim 9, wherein thesubstantially smooth liner-to-outer barrel interface is configured anddisposed to condition a fluid flow passing over the combustor linertoward the end cover.
 15. The turbomachine according to claim 14,wherein stepped lip portion is configured and disposed to promote asubstantially laminar flow across the substantially smooth liner toouter barrel interface.
 16. The turbomachine according to claim 9,wherein the liner stop is provided on the outer barrel member.
 17. Amethod of joining a cap assembly to a turbomachine combustor housing,the method comprising: aligning an outer barrel member carried by thecap assembly with a combustor liner extending about a combustion chamberin the combustor housing; inserting a stepped lip portion provided onone of the outer barrel member and the combustor liner into the other ofthe outer barrel member and the combustor liner to form a liner to outerbarrel interface; and securing the cap assembly to the turbomachinecombustor housing.
 18. The method of claim 17, further comprising:sealing the liner to outer barrel interface.
 19. The method of claim 17,wherein inserting the stepped lip portion provided on one of the outerbarrel member and the combustor liner into the other of the outer barrelmember and the combustor liner includes compressing seal provided on thestepped lip portion.
 20. The method of claim 17, further comprising:restricting axial movement of the combustor liner relative to the outerbarrel member with the stepped lip portion.